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The starting process in a hypersonic nozzle

Published online by Cambridge University Press:  28 March 2006

C. Edward Smith
C. Edward Smith
Affiliation:
Department of Engineering Science, University of Oxford, England and Lockheed Missiles and Space Company, Palo Alto, California
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Abstract

This paper describes an experimental study of the starting process in a reflected-shock tunnel, and compares the results with numerical calculations reported previously (Smith 1962). It is shown that an unsteady expansion wave dominates the transient flow, and the shock-wave system plays a minor role. The effects of initial pressure in the nozzle were investigated, and the behaviour of the secondary shock wave was noted. It was found that initial pressures larger even than the steady-flow static pressure can be tolerated without prolonging the starting process, despite the presence of a strong secondary shock wave. Other analyses, based on the ‘steady-state’ model of the starting process, are discussed and shown to give an unrealistic description of the flow field.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 24 , Issue 4 , April 1966 , pp. 625 - 640
Copyright
© 1966 Cambridge University Press

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